EP2567184A1 - Projectile having a wing guide mechanism - Google Patents

Projectile having a wing guide mechanism

Info

Publication number
EP2567184A1
EP2567184A1 EP11713700A EP11713700A EP2567184A1 EP 2567184 A1 EP2567184 A1 EP 2567184A1 EP 11713700 A EP11713700 A EP 11713700A EP 11713700 A EP11713700 A EP 11713700A EP 2567184 A1 EP2567184 A1 EP 2567184A1
Authority
EP
European Patent Office
Prior art keywords
projectile
wings
wing
sealing element
projectile body
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP11713700A
Other languages
German (de)
French (fr)
Other versions
EP2567184B1 (en
Inventor
Christian Baumann
Thomas Heitmann
Mathias Köhler
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rheinmetall Waffe Munition GmbH
Original Assignee
Rheinmetall Waffe Munition GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rheinmetall Waffe Munition GmbH filed Critical Rheinmetall Waffe Munition GmbH
Publication of EP2567184A1 publication Critical patent/EP2567184A1/en
Application granted granted Critical
Publication of EP2567184B1 publication Critical patent/EP2567184B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor
    • F42B14/064—Sabots enclosing the rear end of a kinetic energy projectile, i.e. having a closed disk shaped obturator base and petals extending forward from said base
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor
    • F42B14/067—Sealing aspects in sabots, e.g. sealing between individual segments of the sabots or sealing between the outer surface of the sabot and the inner surface of the barrel

Definitions

  • the invention relates to a wing-guided projectile, which can be fired, in particular, from a smooth-bore weapon, having a subcaliber projectile body, at the rear end of which a wing control unit comprising several wings is arranged.
  • a projectile to be fired from a smooth tube is known, for example, from the document DE 17 03 507 A1. It essentially comprises a rear side firmly arranged on the projectile body sub-caliber wing saddle and a segmented ejectable center or Zweiflansch-sabot, which is connected for transmitting the acceleration forces exerted on him via positive-locking zones with the subcaliber bullet body. As soon as the projectile has left the mouth of the corresponding weapon barrel, the sabot segments separate themselves from the air pressure acting on them and fly laterally to the ground.
  • a sabot projectile in which the subcaliber projectile body is connected on the rear side with a conical structure.
  • the sabot is in this case a shock-absorbing cage, ie the gas pressure forces generated in a corresponding weapon tube act on a rear side arranged on the projectile body driving element, which then presses against the conical structure and pushes the projectile body from the corresponding gun barrel.
  • the drive element is connected to a drop-down guide cage.
  • a wing-stabilized missile in which the wings of the tail each about a bearing axis of a retracted rest position in which they are arranged parallel to the projectile body and are supported on this, in an outwardly folded flight position are pivotable.
  • WO 02/06761 A describes a wing-stabilized missile to be fired from a pipe, which has at its tail Leittechnikeriel, which takes place from a sub-caliber placement position in one. At the rear of the missile, a fuse box covering the wings is provided, by means of which the tail wings are held in their position of movement.
  • DE 102 05 043 A describes a swirl-stabilized missile to be fired from a tube, which has tail wings at its tail, which can be moved from a sub-caliber position of movement into an over-caliber functional position.
  • a pot bottom and a pot coat having backup pot is provided at the rear of the missile by means of which the tail wings are held in their position of movement.
  • a pressure chamber is provided which is supplied with propellant gases such that the fuse plug of the Leittechnik- wings in their position of transfer holding position along a defined path in a tail wings in their working position releasable release position is adjustable. The fuse plug remains in the release position at the rear of the missile.
  • DE 100 15 514 A1 discloses a missile which can be fired from a tube and has tail wings at its rear, which can be moved from a sub-caliber position of displacement into a super-caliber functional position.
  • At the rear of the missile is an axially displaceable recording.
  • the receptacle serves to accommodate the tail wings and releases this when it has been adjusted in a release position releasing the tail wings in their functional position.
  • the invention has for its object to provide a projectile with a wing-stabilized, sub-caliber projectile body, the launch of a hazard to persons is avoided by flying parts of a sabot.
  • the invention is based essentially on the idea to use a projectile with a rear side fixed to the subcaliber projectile body, about the same caliber drive element (pusher plate - Vollkaliberteil) to use where the wings of the tail are arranged hinged.
  • the drive element should be firmly mounted and serve in addition to the function of a fastener and the acceleration and receiving element for the wings.
  • the respective width of the wings is selected such that the wings in their rest position one or the (actual) guide cage for guiding the projectile body within the gun barrel, from which the projectile is to be fired form.
  • the wings thus replace the state launching a front guide in the pipe by a turned-guide diameter and cause the state before the pipe unfolding and the air attack point for bringing back the wings for aerodynamically stable flight.
  • the omission of a front guide ring causes a shift of the air attack point, which advantageously causes a stable outer ballistics.
  • dead mass is saved in comparison to (ALP) full-caliber bullets, which makes less drive power necessary and thus saves on propellant charge powder.
  • the wings fulfill several tasks - guidance in the pipe, tail in front of the pipe - the bullet is cost-saving. In the area of 100 -500 m in front of the pipe, the risk of injury is minimized by falling parts, prevented by propellant charge cages, etc.
  • the driving element of the projectile is nem annular Dichtungselement- in the wing length at least slightly - enclosed, which on the one hand prevents blowing gas between the driving element and the inner wall of the gun barrel can flow past the projectile, and on the other hand, the wingtips of the wing located in its rest position encloses the outside and holds in their rest positions ,
  • the annular sealing element can be, for example, a sealing strip or a (short) hood made of plastic, which can be pushed over the wings on the rear side.
  • the seal is thus effected by a correspondingly shaped hood, which also serves as a sealing strip.
  • the bearing axes of the wings as seen in the weft direction, arranged behind the front end of the annular sealing element, so that the wings when they are unfolded can optionally push down the optionally provided with predetermined breaking points sealing element of the driving element.
  • FIG. 1 is a side view of a projectile according to the invention with a folding tail, wherein the wings of the tail are in their retracted position of rest, and
  • FIG. 1 shows a longitudinal section through the projectile shown in Figure 1 along the section line II-II.
  • FIGS. 1 and 2 designates a projectile which can be fired from a gun, not shown, which comprises a subcaliber projectile body 2 around which the weapon barrel, likewise not shown, is enclosed.
  • a substantially equal-caliber disk-shaped driving element 3 is arranged on the rear side, on which a wing-laying unit 5 consisting of, for example, four wings 4 is fastened.
  • the wings 4 are each about a located in a recess 6 of the driving element 3 bearing axis 7 of a folded in the rest position shown in Figures 1 and 2, in which they are parallel to the projectile body. 2 are arranged and supported on this, in an outwardly folded flight position swiveled.
  • the wings 4 protrude in the folded state through the recesses 6 in the driving element 3 and preferably have the same outer contour as the driving element 3.
  • the width B of the wings 4 is in each case in a section 8, which is greater than 50% of the length of the wings 4 in the illustrated embodiment, chosen such that lie at the located in its rest position wings 4, the outer sides 9 on a cylinder jacket, corresponding to the corresponding bullet caliber (119.83 to 119.65 - for example, 119.8 mm). This ensures that the wings 4 when firing from a gun barrel on the outside of a gun barrel (for example, with a caliber of 120 mm) are supported and cause a leadership of the subcaliber projectile body 2 within the gun barrel.
  • the wings 4 are held in their rest position by a hood-shaped sealing element 10 made of plastic, which simultaneously prevents the firing of the projectile 1 that propellant charge gases between the driving element 3 and the inner wall of the gun barrel can flow past the projectile 1.
  • the bearing shafts 7 of the wings are arranged behind the front end 12 of the annular sealing element 10.
  • the corresponding cartridge is loaded with the projectile 1 in the tank gun, and ignited by pressing a firing button, the propellant charge of the cartridge.
  • the resulting propellant charge gases then act on the drive element 3 of the projectile 1, which pushes the subcaliber projectile body 2 to the muzzle.
  • the subcaliber projectile body 2 is based on the one hand on the rear side via the sealing element 10 located on the driving element 3 and in the adjoining section 8 via the outer sides 9 of the wings 4 on the inner wall of the corresponding weapon barrel.
  • the wings 4 are activated by the dynamic pressure acting on the front end regions 11 of the wings 4 pivoted outwards in their flight position and thereby push the sealing element 10 rear side away from the driving element 3, ie, the sealing element 10, for example a plastic sealing / sealing tape which holds the wings, is blown up in front of the mouth and in the vicinity of the mouth slowed down the air attack forces.
  • the sealing element 10 for example a plastic sealing / sealing tape which holds the wings, is blown up in front of the mouth and in the vicinity of the mouth slowed down the air attack forces.
  • the wing pivots are in the weft direction behind the sealing strip.

Abstract

The invention relates to a projectile (1) that can be shot from a barreled weapon, comprising a subcaliber projectile body (2), on the rear end of which a wing guide mechanism (5) comprising several wings (4) is arranged. In order to avoid putting persons at risk due to sabot segments that fly away when such projectiles (1) are fired, a driving element (3) of approximately the same caliber is rigidly arranged at the rear on the subcaliber projectile body (2). The wings (4) are foldably arranged on the driving element. The width (B) of the wings (4) is selected in such a way that, in the resting position of the wings, the wings (4) form a guide cage for guiding the projectile body (2) within the weapon barrel from which the projectile (1) is to be shot.

Description

BESCHREIBUNG  DESCRIPTION
Geschoss mit einem Flügelleitwerk Projectile with a wing control
Die Erfindung betrifft ein aus insbesondere einer Glattrohrwaffe verschießbares flügelgeführtes Geschoss mit einem unterkalibrigen Geschosskörper, an dessen heckseitigem Ende ein mehrere Flügel umfassendes Flügelleitwerk angeordnet ist. The invention relates to a wing-guided projectile, which can be fired, in particular, from a smooth-bore weapon, having a subcaliber projectile body, at the rear end of which a wing control unit comprising several wings is arranged.
Ein aus einem Glattrohr zu verschießendes Geschoss ist beispielsweise aus dem Dokument DE 17 03 507 A1 bekannt. Es umfasst im Wesentlichen ein heckseitig fest an dem Geschosskörper angeordnetes unterkalibriges Flügelleitwerk und einen segmentierten abwerfbaren Mitten- oder Zweiflansch-Treibkäfig, der zur Übertragung der auf ihn ausgeübten Beschleunigungskräfte über Formschlusszonen mit dem unterkalibrigen Geschosskörper verbunden ist. Sobald das Geschoss die Mündung des entsprechenden Waffenrohres verlassen hat, trennen sich die Treibkäfigsegmente durch den auf sie wirkenden Staudruck der Luft und fliegen seitlich zu Boden. A projectile to be fired from a smooth tube is known, for example, from the document DE 17 03 507 A1. It essentially comprises a rear side firmly arranged on the projectile body sub-caliber wing saddle and a segmented ejectable center or Zweiflansch-sabot, which is connected for transmitting the acceleration forces exerted on him via positive-locking zones with the subcaliber bullet body. As soon as the projectile has left the mouth of the corresponding weapon barrel, the sabot segments separate themselves from the air pressure acting on them and fly laterally to the ground.
Nachteilig ist bei diesen bekannten Treibkäfiggeschossen unter anderem, dass sie aufgrund der Verwendung des Treibkäfigs ein relativ hohes Totgewicht besitzen. Außerdem werden insbesondere bei Verwendung von Panzerwaffen durch den Abwurf der Treibkäfigsegmente im Rohrmündungsbereich der entsprechenden Waffe die eigenen Soldaten (Infanteristen) gefährdet, wenn sich diese, etwa bei einem Häuserkampf, im Bereich des entsprechenden Kampfpanzers befinden. A disadvantage of these known sabot projectiles, inter alia, that they have a relatively high dead weight due to the use of the sabot. In addition, especially when using armored weapons by the dropping of the sabot segments in the muzzle area of the corresponding weapon your own soldiers (infantrymen) endangered if they are, such as in a house fight, in the field of the corresponding main battle tank.
Aus dem Dokument DE 10 2008 049 146 A ist ein Treibkäfiggeschoß bekannt, bei dem der unterkalibrige Geschoßkörper heckseitig mit einem Kegelleitwerk verbunden ist. Bei dem Treibkäfig handelt es sich in diesem Fall um einen Stoßtreibkäfig, d.h. die in einem entsprechenden Waffenrohr erzeugten Gasdruckkräfte wirken auf ein heckseitig an dem Geschosskörper angeordnetes Treibelement, welches dann gegen das Kegelleitwerk drückt und den Geschosskörper aus dem entsprechenden Waffenrohr schiebt. Zur vor- derseitigen Führung des unterkalibrigen Geschoßkörpers innerhalb des Waffenrohres ist das Treibelement mit einem abwerfbaren Führungskäfig verbunden. From the document DE 10 2008 049 146 A a sabot projectile is known in which the subcaliber projectile body is connected on the rear side with a conical structure. The sabot is in this case a shock-absorbing cage, ie the gas pressure forces generated in a corresponding weapon tube act on a rear side arranged on the projectile body driving element, which then presses against the conical structure and pushes the projectile body from the corresponding gun barrel. For the present derseitige leadership of the subcaliber projectile body within the gun barrel, the drive element is connected to a drop-down guide cage.
Weitere Treibkäfiggeschosse betreffen die DE 10 2008 029 397 A, die 10 2008 029 396 A als auch die 10 2008 037 738 A. Further sabot projectiles concern the DE 10 2008 029 397 A, the 10 2008 029 396 A as well as the 10 2008 037 738 A.
Auch bei diesen Geschossen kann es durch das Abwerfen des Treibelementes sowie der Teile des Führungskäfigs zu einer Gefährdung der eigenen, im Bereich einer Panzerkanone befindlichen Truppen kommen. Even with these floors, it can come by the dropping of the drive element and the parts of the guide cage to a threat to their own, located in the range of a tank gun troops.
Schließlich sind aus dem Dokument DE 199 41 555 C1 ein flügelstabilisierte Flugkörper bekannt, bei denen die Flügel des Leitwerkes jeweils um eine Lagerachse von einer eingeklappten Ruheposition, bei der sie parallel zum Geschoßkörper angeordnet sind und sich an diesem abstützen, in eine nach außen geklappte Flugstellung schwenkbar sind. Finally, from the document DE 199 41 555 C1 a wing-stabilized missile is known in which the wings of the tail each about a bearing axis of a retracted rest position in which they are arranged parallel to the projectile body and are supported on this, in an outwardly folded flight position are pivotable.
Die WO 02/06761 A beschreibt einen aus einem Rohr zu verschießenden flügelstabilisierten Flugkörper , der an seinem Heck Leitwerkflügel aufweist, die von einer unterkalibrigen Verbringungsstellung in eine erfolgt. Am Heck des Flugkörpers ist ein die Flügel abdeckender Sicherungstopf vorgesehen, mittels dessen die Leitwerk- Flügel in ihre Verbringungsstellung gehalten werden. WO 02/06761 A describes a wing-stabilized missile to be fired from a pipe, which has at its tail Leitwerkflügel, which takes place from a sub-caliber placement position in one. At the rear of the missile, a fuse box covering the wings is provided, by means of which the tail wings are held in their position of movement.
Die DE 102 05 043 A beschreibt einen aus einem Rohr zu verschießenden drallstabilisierten Flugkörper, der an seinem Heck Leitwerkflügel aufweist, die von einer unterkalibrigen Verbringungsstellung in eine überkalibrige Funktionsstellung bewegbar sind. Am Heck des Flugkörpers ist ein einen Topfboden und einen Topfmantel aufweisenden Sicherungstopf vorgesehen, mittels dessen die Leitwerk- Flügel in ihre Verbringungsstellung gehalten werden. Zwischen der rückseitigen Heckstirnfläche des Flugkörpers und dem Topfboden des Sicherungstopfes ist ein Druckraum vorhanden, der mit Treibladungsgasen versorgt wird derart, dass der Sicherungstopf von der die Leitwerk- Flügel in ihrer Verbringungsstellung haltenden Haltestellung entlang einer definierten Wegstrecke in eine die Leitwerk- Flügel in ihre Funktionsstellung freigebende Freigabestellung verstellbar ist. Dabei verbleibt der Sicherungstopf in der Freigabestellung am Heck des Flugkörpers. Die DE 100 15 514 A1 offenbart ein aus einem Rohr verschießbaren Flugkörper, der an seinem Heck Leitwerkflügel aufweist, die von einer unterkalibrigen Verbringungsstellung in eine überkalibrige Funktionsstellung bewegbar sind. Am Heck des Flugkörpers ist eine axial verschiebbare Aufnahme. Die Aufnahme dient zur Aufnahme der Leitwerk- Flügel und gibt dieser frei, wenn sie in eine die Leitwerk- Flügel in ihre Funktionsstellung freigebende Freigabestellung verstellt worden ist. DE 102 05 043 A describes a swirl-stabilized missile to be fired from a tube, which has tail wings at its tail, which can be moved from a sub-caliber position of movement into an over-caliber functional position. At the rear of the missile, a pot bottom and a pot coat having backup pot is provided by means of which the tail wings are held in their position of movement. Between the rear tail end face of the missile and the pot bottom of the fuse plug, a pressure chamber is provided which is supplied with propellant gases such that the fuse plug of the Leitwerk- wings in their position of transfer holding position along a defined path in a tail wings in their working position releasable release position is adjustable. The fuse plug remains in the release position at the rear of the missile. DE 100 15 514 A1 discloses a missile which can be fired from a tube and has tail wings at its rear, which can be moved from a sub-caliber position of displacement into a super-caliber functional position. At the rear of the missile is an axially displaceable recording. The receptacle serves to accommodate the tail wings and releases this when it has been adjusted in a release position releasing the tail wings in their functional position.
Der Erfindung liegt die Aufgabe zugrunde, ein Geschoss mit einem flügelstabilisierten, unterkalibrigen Geschosskörper anzugeben, bei dessen Abschuß eine Gefährdung von Personen durch wegfliegende Teile eines Treibkäfigs vermieden wird. The invention has for its object to provide a projectile with a wing-stabilized, sub-caliber projectile body, the launch of a hazard to persons is avoided by flying parts of a sabot.
Diese Aufgabe wird erfindungsgemäß durch die Merkmale des Anspruchs 1 gelöst. Weitere, besonders vorteilhafte Ausgestaltungen der Erfindung offenbaren die Unteransprüche. This object is achieved by the features of claim 1. Further, particularly advantageous embodiments of the invention disclose the dependent claims.
Die Erfindung beruht im Wesentlichen auf dem Gedanken, ein Geschoss mit einem heck- seitig an dem unterkalibrigen Geschosskörper fest angeordneten, etwa kalibergleichen Treibelement (Pusherplatte - Vollkaliberteil) zu verwenden, an dem die Flügel des Leitwerkes klappbar angeordnet sind. Das Treibelement sollte fest montiert sein und neben der Funktion eines Befestigungselementes auch die des Beschleunigungs- und Aufnahmeelement für die Flügel dienen. Dabei ist die jeweilige Breite der Flügel derart gewählt, dass die Flügel in ihrer Ruheposition einen bzw. den (eigentlichen) Führungskäfig zur Führung des Geschoßkörpers innerhalb des Waffenrohres, aus dem das Geschoss verschossen werden soll, bilden. Die Flügel ersetzen somit beim Zustand Abschuss eine vordere Führung im Rohr durch einen angedrehten Führungsdurchmesser und bewirken beim Zustand vor dem Rohr das Aufklappen sowie den Luftangriffspunkt für das nach hinten bringen der Flügel für einen aerodynamisch stabilen Flug. Das Weglassen eines vorderen Führungsringes bewirkt eine Verlagerung des Luftangriffspunkt, was vorteilhaft eine stabile Außenballistik bewirkt. Des Weiteren wird Totmasse im Vergleich zu (ALP-) Vollkalibergeschossen eingespart, was weniger Antriebsleistung notwendig macht und damit Einsparung von Treibladungspulver. Da die Flügel mehrere Aufgaben erfüllen - Führung im Rohr, Leitwerk vor dem Rohr - ist das Geschoss kostensparender. Im Bereich von 100 -500 m vor dem Rohr wird die Verletzungsgefahr durch herabfallende Teile minimiert, von Treibladungskäfige etc. verhindert. The invention is based essentially on the idea to use a projectile with a rear side fixed to the subcaliber projectile body, about the same caliber drive element (pusher plate - Vollkaliberteil) to use where the wings of the tail are arranged hinged. The drive element should be firmly mounted and serve in addition to the function of a fastener and the acceleration and receiving element for the wings. In this case, the respective width of the wings is selected such that the wings in their rest position one or the (actual) guide cage for guiding the projectile body within the gun barrel, from which the projectile is to be fired form. The wings thus replace the state launching a front guide in the pipe by a turned-guide diameter and cause the state before the pipe unfolding and the air attack point for bringing back the wings for aerodynamically stable flight. The omission of a front guide ring causes a shift of the air attack point, which advantageously causes a stable outer ballistics. Furthermore, dead mass is saved in comparison to (ALP) full-caliber bullets, which makes less drive power necessary and thus saves on propellant charge powder. Since the wings fulfill several tasks - guidance in the pipe, tail in front of the pipe - the bullet is cost-saving. In the area of 100 -500 m in front of the pipe, the risk of injury is minimized by falling parts, prevented by propellant charge cages, etc.
Bei einer bevorzugten Ausführungsform wird das Treibelement des Geschosses von ei- nem ringförmigen Dichtungselement- in der Flügellänge zumindest geringfügig - umschlossen, welches einerseits verhindert, dass Treibladungsgase zwischen dem Treibelement und der Innenwand des Waffenrohres an dem Geschoß vorbeiströmen können, und welches andererseits die Flügelenden der in ihrer Ruheposition befindlichen Flügel außenseitig umschließt und in ihren Ruhepositionen hält. In a preferred embodiment, the driving element of the projectile is nem annular Dichtungselement- in the wing length at least slightly - enclosed, which on the one hand prevents blowing gas between the driving element and the inner wall of the gun barrel can flow past the projectile, and on the other hand, the wingtips of the wing located in its rest position encloses the outside and holds in their rest positions ,
Bei dem ringförmigen Dichtungselement kann es sich beispielsweise um ein Dichtungsband oder eine (Kurz-)Haube aus Kunststoff handeln, welche heckseitig über die Flügel aufschiebbar ist. Die Abdichtung erfolgt somit durch eine entsprechend geformte Haube, welche gleichzeitig als Dichtungsband dient. The annular sealing element can be, for example, a sealing strip or a (short) hood made of plastic, which can be pushed over the wings on the rear side. The seal is thus effected by a correspondingly shaped hood, which also serves as a sealing strip.
Vorzugsweise sind die Lagerachsen der Flügel, in Schußrichtung gesehen, hinter dem vorderen Ende des ringförmigen Dichtungselementes angeordnet, sodass die Flügel bei ihrem Aufklappen das gegebenenfalls mit Sollbruchstellen versehene Dichtungselement heckseitig von dem Treibelement herunterschieben können. Preferably, the bearing axes of the wings, as seen in the weft direction, arranged behind the front end of the annular sealing element, so that the wings when they are unfolded can optionally push down the optionally provided with predetermined breaking points sealing element of the driving element.
Weitere Einzelheiten und Vorteile der Erfindung ergeben sich aus den folgenden, anhand von Figuren erläuterten Ausführungsbeispielen. Es zeigen: Further details and advantages of the invention will become apparent from the following, with reference to figures explained embodiments. Show it:
Fig.1 die Seitenansicht eines erfindungsgemäßen Geschosses mit einem Klappleitwerk, wobei sich die Flügel des Leitwerkes in ihrer eingeklappten Ruheposition befinden, und 1 is a side view of a projectile according to the invention with a folding tail, wherein the wings of the tail are in their retracted position of rest, and
Fig.2 einen Längsschnitt durch das in Fig.1 dargestellte Geschoß entlang der dort mit II- II bezeichneten Schnittlinie. 1 shows a longitudinal section through the projectile shown in Figure 1 along the section line II-II.
In den Fig.1 und 2 sind mit 1 ein aus einer nicht dargestellten Rohrwaffe verschießbares Geschoss bezeichnet, welches einen unterkalibrigen Geschosskörper 2 umfasst um vom ebenfalls nicht näher dargestellten Waffenrohr umfasst wird. In FIGS. 1 and 2, 1 designates a projectile which can be fired from a gun, not shown, which comprises a subcaliber projectile body 2 around which the weapon barrel, likewise not shown, is enclosed.
An dem Geschosskörper 2 ist heckseitig ein im Wesentlichen kalibergleiches scheibenförmiges Treibelement 3 angeordnet, an dem ein aus beispielsweise vier Flügeln 4 bestehendes Flügelleitwerk 5 befestigt ist. Dabei sind die Flügel 4 jeweils um eine in einer Aussparung 6 des Treibelementes 3 befindlichen Lagerachse 7 von einer in den Fig.1 und 2 dargestellten eingeklappten Ruheposition, bei der sie parallel zu dem Geschosskörper 2 angeordnet sind und sich an diesem abstützen, in eine nach außen geklappte Flugstellung verschwenkbar. Die Flügel 4 ragen im eingeklappten Zustand durch die Aussparungen 6 in das Treibelement 3 und weisen vorzugsweise die gleiche Außenkontur wie das Treibelement 3 auf. On the projectile body 2, a substantially equal-caliber disk-shaped driving element 3 is arranged on the rear side, on which a wing-laying unit 5 consisting of, for example, four wings 4 is fastened. The wings 4 are each about a located in a recess 6 of the driving element 3 bearing axis 7 of a folded in the rest position shown in Figures 1 and 2, in which they are parallel to the projectile body. 2 are arranged and supported on this, in an outwardly folded flight position swiveled. The wings 4 protrude in the folded state through the recesses 6 in the driving element 3 and preferably have the same outer contour as the driving element 3.
Die Breite B der Flügel 4 ist jeweils in einem Teilabschnitt 8, der bei dem dargestellten Ausführungsbeispiel größer als 50 % der Länge der Flügel 4 beträgt, derart gewählt, dass bei den in ihrer Ruheposition befindlichen Flügeln 4, die Außenseiten 9 auf einem Zylindermantel liegen, der dem entsprechenden Geschosskaliber (119,83 bis 119,65 - beispielsweise 119,8 mm) entspricht. Dadurch wird erreicht, dass sich die Flügel 4 beim Abschuß aus einer Rohrwaffe außenseitig an einem Waffenrohr (beispielsweise mit einem Kaliber von 120 mm) abstützen und eine Führung des unterkalibrigen Geschosskörpers 2 innerhalb des Waffenrohres bewirken. The width B of the wings 4 is in each case in a section 8, which is greater than 50% of the length of the wings 4 in the illustrated embodiment, chosen such that lie at the located in its rest position wings 4, the outer sides 9 on a cylinder jacket, corresponding to the corresponding bullet caliber (119.83 to 119.65 - for example, 119.8 mm). This ensures that the wings 4 when firing from a gun barrel on the outside of a gun barrel (for example, with a caliber of 120 mm) are supported and cause a leadership of the subcaliber projectile body 2 within the gun barrel.
Die Flügel 4 werden in ihrer Ruheposition durch ein haubenförmiges Dichtungselement 10 aus Kunststoff gehalten, welches gleichzeitig beim Abschuß des Geschosses 1 verhindert, dass Treibladungsgase zwischen dem Treibelement 3 und der Innenwand des Waffenrohres an dem Geschoss 1 vorbeiströmen können. The wings 4 are held in their rest position by a hood-shaped sealing element 10 made of plastic, which simultaneously prevents the firing of the projectile 1 that propellant charge gases between the driving element 3 and the inner wall of the gun barrel can flow past the projectile 1.
Wie aus Fig.2 unmittelbar entnehmbar ist, sind die Lagerachsen 7 der Flügel 4, in Schußrichtung gesehen, hinter dem vorderen Ende 12 des ringförmigen Dichtungselementes 10 angeordnet. As can be seen directly from FIG. 2, the bearing shafts 7 of the wings 4, viewed in the weft direction, are arranged behind the front end 12 of the annular sealing element 10.
Zum Verschießen des erfindungsgemäßen Geschosses 1 , etwa aus einer Panzerkanone, wird die entsprechende Patrone mit dem Geschoss 1 in die Panzerkanone geladen, und durch Betätigung einer Abfeuertaste die Treibladung der Patrone gezündet. Die entstehenden Treibladungsgase wirken dann auf das Treibelement 3 des Geschosses 1 , welches den unterkalibrigen Geschosskörper 2 zur Rohrmündung hinschiebt. Dabei stützt sich der unterkalibrige Geschosskörper 2 einerseits heckseitig über das auf dem Treibelement 3 befindliche Dichtungselement 10 und im sich anschließenden Teilabschnitt 8 über die Außenseiten 9 der Flügel 4 an der Innenwand des entsprechenden Waffenrohres ab. To shoot the projectile 1 according to the invention, such as a tank gun, the corresponding cartridge is loaded with the projectile 1 in the tank gun, and ignited by pressing a firing button, the propellant charge of the cartridge. The resulting propellant charge gases then act on the drive element 3 of the projectile 1, which pushes the subcaliber projectile body 2 to the muzzle. Here, the subcaliber projectile body 2 is based on the one hand on the rear side via the sealing element 10 located on the driving element 3 and in the adjoining section 8 via the outer sides 9 of the wings 4 on the inner wall of the corresponding weapon barrel.
Sobald das Geschoss 1 die Mündung des Waffenrohres verlassen hat, werden durch den auf die vorderen Endbereiche 11 der Flügel 4 wirkenden Staudruck der Luft die Flügel 4 nach außen in ihre Flugstellung verschwenkt und schieben dabei das Dichtungselement 10 heckseitig von dem Treibelement 3 weg, d.h., das Dichtungselement 10, beispielsweise ein Kunststoffdichtungs-/-abdichtungsband, welches die Flügel hält, wird vor der Mündung gesprengt und im Nahbereich vor der Mündung durch die Luftangriffskräfte abgebremst. Die Flügeldrehpunkte liegen in Schussrichtung hinter dem Dichtungsband. As soon as the projectile 1 has left the mouth of the weapon barrel, the wings 4 are activated by the dynamic pressure acting on the front end regions 11 of the wings 4 pivoted outwards in their flight position and thereby push the sealing element 10 rear side away from the driving element 3, ie, the sealing element 10, for example a plastic sealing / sealing tape which holds the wings, is blown up in front of the mouth and in the vicinity of the mouth slowed down the air attack forces. The wing pivots are in the weft direction behind the sealing strip.
Es versteht sich, dass im Rahmen der Erfindung Anpassungen möglich sind. So ist die Anzahl der Flügel variabel. Des Weiteren kann auch ein vorderer Führungsring über die Flügel gezogen werden, der abscherend angebracht ist. Auch können die Flügeldrehpunkte verändert werden, wenn auf einen anderen Öffnungsmechanismus als die Zentrifugalkraft zurückgegriffen wird. It is understood that adjustments are possible within the scope of the invention. So the number of wings is variable. Furthermore, a front guide ring can be pulled over the wings, which is mounted schscherend. Also, the wing pivots can be changed when resorting to a different opening mechanism than the centrifugal force.
Bezugszeichenliste LIST OF REFERENCE NUMBERS
1 Geschoss 1 floor
2 Geschosskörper  2 projectiles
3 Treibelement  3 driving element
4 Flügel  4 wings
5 Flügelleitwerk  5 wing control unit
6 Aussparung  6 recess
7 Lagerachse  7 bearing axis
8 Teilabschnitt  8 subsection
9 Außenseite  9 outside
10 Dichtungselement  10 sealing element
11 Endbereich  11 end area
12 vordere Ende  12 front end
B Breite der Flügel in dem Teilabschnitt 8 B width of the wings in the section 8

Claims

Patentansprüche claims
1. Geschoss (2), das aus einer Rohrwaffe verschießbar ist, mit einem unterkalibrigen Geschosskörper (2), an dessen heckseitigem Ende ein mehrere Flügel (4) umfassendes Flügelleitwerk (5) angeordnet ist, dadurch gekennzeichnet, dass die Flügel (4) derart zum Geschosskörper (2) angebracht sind, dass sie sich an diesem abstützend in eine nach außen geklappte Flugstellung schwenkbar sind, beim Abschuss aus der Rohrwaffe außenseitig an dem Waffenrohr abstützen und eine Führung des Geschoßkörpers (2) innerhalb des Waffenrohres bewirken und an dem Geschosskörper (2) heckseitig ein die Flügel (4) umfassenden ringförmigen Dichtungselement (10) befestigt ist, dass neben der Dichtung des Geschosses (2) zum Rohr die Haltefunktion für die Flügel (4) übernimmt. 1. projectile (2) which can be fired from a gun barrel, with a sub-caliber projectile body (2), at the rear end of which a wing (4) comprehensive wing wire (5) is arranged, characterized in that the wings (4) in such a way to the projectile body (2) are mounted so that they are pivotally supported on this in an outwardly folded flight position, supported during firing from the gun on the outside of the barrel and cause a leadership of the projectile body (2) within the barrel and on the projectile body ( 2) on the rear side, the wing (4) comprehensive annular sealing element (10) is fixed, that in addition to the seal of the projectile (2) to the pipe assumes the holding function for the wing (4).
2. Geschoss nach Anspruch 1 , dadurch gekennzeichnet, dass es im Wesentlichen kalibergleiches scheibenförmiges Treibelement (3) aufweist. 2. Projectile according to claim 1, characterized in that it has substantially the same caliber disc-shaped driving element (3).
3. Geschoss nach Anspruch 2, dadurch gekennzeichnet, dass die Flügel (4) des Flügelleitwerkes (5) jeweils um eine in einer Aussparung (6) des Treibelementes (3) befindlichen Lagerachse (7) von einer eingeklappten Ruheposition, bei der sie parallel zu dem Geschoßkörper (2) angeordnet sind. 3. A projectile according to claim 2, characterized in that the wings (4) of the wing assembly (5) each about a in a recess (6) of the drive element (3) located bearing axis (7) of a retracted rest position, in which they are parallel to the projectile body (2) are arranged.
4. Geschoss nach Anspruch 3, dadurch gekennzeichnet, dass die Breite (B) der Flügel (4) ist jeweils mindestens in einem Teilabschnitt (8) derart gewählt, dass bei den in ihrer Ruheposition befindlichen Flügeln (4) die Außenseiten (9) der Flügel (4) auf einem Zylindermantel mit kalibergleichem Durchmesser liegen. 4. Projectile according to claim 3, characterized in that the width (B) of the wing (4) is in each case at least in a section (8) chosen such that at the located in its rest position wings (4) the outer sides (9) of Wing (4) lie on a cylinder jacket with caliber same diameter.
5. Geschoss nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass das ringförmige Dichtungselement (10) die Flügelenden der in ihrer Ruheposition befindlichen Flügel (4) außenseitig umschließt und in ihren Ruhepositionen hält. 5. Projectile according to one of claims 1 to 4, characterized in that the annular sealing element (10) surrounds the wing ends of the located in its rest position wings (4) on the outside and holds in their rest positions.
6. Geschoss nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass es sich bei dem ringförmigen Dichtungselement (10) um ein aus Kunststoff bestehendes Dichtungsband handelt. 6. Projectile according to one of claims 1 to 5, characterized in that it is in the annular sealing element (10) is an existing plastic sealing strip.
7. Geschoss nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass es sich bei dem ringförmigen Dichtungselement (10) um eine aus Kunststoff bestehende Haube handelt, welche heckseitig auf das Treibelement (3) aufschiebbar ist. 7. Projectile according to one of claims 1 to 6, characterized in that it is in the annular sealing element (10) is a plastic hood, which on the rear side of the drive element (3) can be pushed.
8. Geschoss nach einem der Ansprüche 3 bis 7, dadurch gekennzeichnet, dass die Lagerachsen (7) der Flügel (4), in Schußrichtung gesehen, hinter dem vorderen Ende (12) des ringförmigen Dichtungselementes (10) angeordnet sind. 8. Projectile according to one of claims 3 to 7, characterized in that the bearing axes (7) of the wings (4), seen in the weft direction, behind the front end (12) of the annular sealing element (10) are arranged.
EP11713700.0A 2010-05-04 2011-04-08 Projectile having a wing guide mechanism Not-in-force EP2567184B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE201010019384 DE102010019384A1 (en) 2010-05-04 2010-05-04 Projectile with a wing control
PCT/EP2011/001748 WO2011137958A1 (en) 2010-05-04 2011-04-08 Projectile having a wing guide mechanism

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EP2567184A1 true EP2567184A1 (en) 2013-03-13
EP2567184B1 EP2567184B1 (en) 2014-11-05

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WO (1) WO2011137958A1 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014035518A2 (en) * 2012-06-07 2014-03-06 Aerovironment, Inc. System for detachably coupling an unmanned aerial vehicle within a launch tube
RU2707625C1 (en) * 2019-02-14 2019-11-28 Федеральное государственное казенное военное образовательное учреждение высшего образования "ВОЕННАЯ АКАДЕМИЯ МАТЕРИАЛЬНО-ТЕХНИЧЕСКОГО ОБЕСПЕЧЕНИЯ имени генерала армии А.В. Хрулева" Sub-caliber cluster rocket shot
CN114750336B (en) * 2022-06-15 2022-09-13 中国飞机强度研究所 Method for manufacturing missile support system of ground simulation test for airplane strength test

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2008535A1 (en) * 1968-05-15 1970-01-23 Diehl Fa Stabilised missile propulsion system
DE2603756A1 (en) * 1976-01-31 1977-08-04 Rheinmetall Gmbh LOWER CALIBER FLOOR WITH STABILIZING WINGS
DE3309533A1 (en) * 1983-03-17 1984-09-20 Diehl GmbH & Co, 8500 Nürnberg WING-STABILIZED SHELL WITH DRIVING CAGE
FR2768809B1 (en) * 1997-09-24 1999-10-15 Giat Ind Sa LARGE CALIBER LONG RANGE FIELD ARTILLERY PROJECTILE
DE19941555C5 (en) 1999-09-01 2004-12-30 Rheinmetall W & M Gmbh missile
DE10015514B4 (en) 2000-03-30 2007-10-04 Rheinmetall Waffe Munition Gmbh Wing stabilized projectile
SE518657C2 (en) 2000-07-03 2002-11-05 Bofors Defence Ab Fine stabilized steerable projectile
DE10115088A1 (en) * 2001-03-27 2002-10-02 Rheinmetall W & M Gmbh Projectile used as tank ammunition comprises tail unit with folding wings rotatably connected to holding element for holding tail unit in folded position
DE10205043C5 (en) 2002-02-07 2010-06-17 Diehl Bgt Defence Gmbh & Co. Kg From a tube to be closed missile with überkalibrigem tail
DE102008029397A1 (en) 2008-06-23 2009-12-24 Rheinmetall Waffe Munition Gmbh Sabot projectile
DE102008029396A1 (en) 2008-06-23 2009-12-24 Rheinmetall Waffe Munition Gmbh Sabot projectile
DE102008037738B4 (en) 2008-08-14 2010-06-24 Sew-Eurodrive Gmbh & Co. Kg Electrical plug connection and electrical device
DE102008049146A1 (en) 2008-09-26 2010-04-01 Rheinmetall Waffe Munition Gmbh Sabot projectile

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2011137958A1 *

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WO2011137958A1 (en) 2011-11-10
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